An arrangement for electrically powering an aircraft comprises at least one first generator driven by an engine of the aircraft, an electricity network on board the aircraft receiving the voltage produced by the first generator, at least one second generator driven by the motor, and an engine electrical network distinct from the on-board network for powering equipment of the engine of its environment, the engine network comprising:
Legal claims defining the scope of protection, as filed with the USPTO.
1. An arrangement for electrically powering an aircraft, the arrangement comprising: at least one first generator supplying an electrical voltage on being driven by an engine of the aircraft; an electrical power distribution network on board the aircraft connected to the first generator via a power supply line to receive the electrical voltage produced by the first generator; at least one second generator supplying an electrical voltage on being driven by an engine of the aircraft; and an electrical power distribution network of the aircraft engine that is distinct from the on-board network and that serves to supply electrical power to electrical equipment situated in the aircraft engine and/or in the environment of the engine, the engine network comprising: at least one bus for distributing DC electrical voltage for the electrical equipment; and a power supply circuit having a first input connected to the on-board network to receive a voltage supplied by the on-board network, a second input connected to the second generator to receive the electrical voltage supplied thereby, a voltage converter connected to the second input, and a selector circuit for delivering a voltage over the distribution bus, which voltage is supplied from the voltage received on the first input, or is supplied by the converter, depending on the amplitude of the voltage supplied by the second generator.
2. An arrangement according to claim 1 , wherein the power supply circuit of the engine network further includes a voltage converter connected to the first input to convert the voltage supplied by the on-board network.
3. An arrangement according to claim 1 , wherein the voltage distribution bus of the engine network is a regulated DC voltage distribution bus.
4. An arrangement according to claim 1 , wherein at least one set of modules is provided with inverters powered by the DC voltage distribution bus, and delivering an alternating voltage to the electrical equipment.
5. An arrangement according to claim 1 , having two second electricity generators driven by the engine and respectively connected to the second input and to the third input of the power supply circuit, and two voltage distribution buses connected to a first output and to a second output of the power supply arrangement, and the power supply circuit further includes a voltage converter connected to the third input, the voltage converters connected to the second and third inputs being connected respectively to the first output and to the second output.
6. An arrangement according to claim 5 , wherein the first input is connected to the first and second outputs of the power supply circuit, the selector circuit serving to supply voltages on the first and second distribution buses, which voltages are supplied respectively by the converters connected to the second and third inputs, or from the voltage received on the first input.
7. An arrangement according to claim 1 , wherein the, or each, second generator is a permanent magnet alternator.
8. An arrangement according to claim 1 , wherein the electrical equipment includes electromechanical actuators for parts of the engine that are of variable geometry, and electric motors for pumps.
9. An arrangement according to claim 1 , wherein the electrical equipment includes at least one circuit for de-icing the engine pod.
10. An arrangement according to claim 1 , for an airplane engine, wherein the electrical equipment includes at least one circuit for de-icing the wing supporting the engine.
11. An arrangement according to claim 1 , for a gas turbine airplane engine, wherein the electrical equipment includes electrically actuated electromechanical actuators of a thrust reverser.
Cooperative Patent Classification codes for this invention. Click any code to explore related patents in that topic.
May 3, 2007
May 26, 2009
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